US3192708A - Rocket motors - Google Patents

Rocket motors Download PDF

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Publication number
US3192708A
US3192708A US133659A US13365961A US3192708A US 3192708 A US3192708 A US 3192708A US 133659 A US133659 A US 133659A US 13365961 A US13365961 A US 13365961A US 3192708 A US3192708 A US 3192708A
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US
United States
Prior art keywords
port
igniter
charge
septum
partition
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US133659A
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English (en)
Inventor
Nicolson William Hugh
Doyle Wilfred
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Imperial Chemical Industries Ltd
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Imperial Chemical Industries Ltd
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Publication date
Application filed by Imperial Chemical Industries Ltd filed Critical Imperial Chemical Industries Ltd
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Publication of US3192708A publication Critical patent/US3192708A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements

Definitions

  • the present invention relates to rocket motors of the kind comprising at least two solid propellant charges which are required to be ignited substantially simultaneously, for example, a boost charge designed to accelerate the rocket to a pre-determined speed and a sustainer charge designed to maintain the rocket at or about the said speed.
  • both charges have hitherto been lit most commonly by separate electricallyfired igniters.
  • Such a practice increases the possibility of failure over what would be the case were both charges to be ignited by a single electrically-fired igniter because of the additional circuitry and components necessary.
  • the object of the present invention is to provide a double chamber dual thrust solid propellant rocket motor wherein ignition of the solid propellant of the second stage is effected without using a separate electrical igniter in its ignition.
  • a rocket motor has two solid propellant charges, two igniters, and a septum or partition, wherein one igniter is for each charge, wherein one charge and its igniter are on one side and the other charge and its igniter are on the other side of the septum, wherein at least one of said igniters is adjacent to said septum, and wherein said septum has a port therethrough communicating with any igniter adjacent said septum to permit such an igniter to be ignited by heat energy resulting from the ignition of the igniter on the other side of the septum.
  • one of the igniters, i.e. that igniter to be first ignited, of the rocket motor is disposed remote from said septum, so in the main it is the heat energy developed by the charge ignited by this igniter which passes through said port to ignite the igniter adjacent the septum.
  • the septum of the rocket motor has an igniter adjacent each side thereof, so it is the heat energy developed by the igniter arranged first to be ignited and by the charge ignited by this igniter which passes through said port to ignite the igniter adjacent the other side of the septum.
  • any igniter adjacent the septum comprises a charge capitively arranged in a container to prevent dispersion of the charge before proper ignition thereof.
  • the igniter to be first ignited may contain an electrical igniter or may be associated with an electrical igniter or with other ignition means.
  • ignition of the first solid propellant charge which will usually be the boost charge is followed by a rise in pressure in the chamber containing the boost charge and will result in a flow of propellant gas through the port.
  • the port may be sufiiciently large to enable the flow of gas to assist in raising the pressure in the second chamber, which will usually contain the sustainer charge, to its desired operating pressure, in which case the port may have an associated valve to close the port and prevent loss of gas through the port in the reverse direction when the boost charge is burnt out. This arrangement is shown in FIGURE 1A where 18 is the valve.
  • the port may have a restricted diameter, for example inch, so that the loss of gas through the port when the first charge is burnt out is unimportant.
  • FIGURE 1 is a fragmentary diagrammatic sectional view of a rocket motor
  • FIGURE 1A is a fragmentary view of part of FIG- URE 1, on an enlarged scale, showing a check valve associated with the port;
  • FIGURE 2 is a diagrammatic sectional veiw of a modified form of the rocket motor of FIGURE 1.
  • the rocket motor illustrated therein comprises a cylindrical body or casing 1 which is divided into two parts by a septum or partition 2 having a port which is filled in as hereinafter indicated.
  • the casing is covered with thermal insulation 13.
  • a solid propellant boost charge 3 and a solid propellant sustainer charge 4 are disposed respectively at opposite sides of the septum 2.
  • a repeat igniter comprising ignition composition 5 carried in a cup 6 which is closed by a retainer disc 7.
  • the cup 6 is held to the septum 2 by a nut 8 engaging with a spigot 9 held to the base of the cup 6.
  • the spigot 9 passes through to fill the aforementioned port of the septum 2 and is bored to form a port iii of restricted diameter.
  • a passage 11 (which is one of a number of such passages) extends lengthwise through the solid propellant boost charge 3 and opens to the septum 2 at one end and to the vicinity of a primary igniter 12 at the other end.
  • the igniter 12 is associated with a primer (not shown) located in a transfer tube 15.
  • the primer ignites the boost igniter 12 which then lights booster charge 3, the gases passing out through a nozzle located in the same relative position as shown in the phantom line in proposed FIGURE 2.
  • a small amount of gas passes down channel 11 and through port 10 in the septum 2 and initiates the sustainer igniter 5. This in turn lights the sustainer charge 4, gas from which passes through the transfer tube 15 to a sustainer nozzle 17.
  • a small quantity of gas is lost from the sustainer portion via the port It to the boost portion.
  • the rocket motor illustrated therein comprises a cylindrical body or casing 1 which is divided into two parts by a septum 2 having a port which is filled in as hereinafter described.
  • a solid propellant boost charge 3 and a solid propellant sustainer charge 4 are disposed respectively at opposite sides of the septum 2.
  • an igniter comprising ignition composition 5 carried in a cup 6 which is closed by a retainer disc 7.
  • the cup 6 is held to the septum 2 by a block 8 engaging with a spigot 9 held to the base of the cup 6.
  • the spigot 9 passes through to fill the aforementioned port of the septum 2 and is bored to form a port 10, one part of which is of restricted diameter.
  • the larger section of this port 10 houses an auxiliary charge of ignition material 11, the port 10 then branches into an annular container 12' attached to the block 8, which container is filled with the main boo-st charge ignition material.
  • the flash from a conventional electric primer 14 which is held in place by a retaining nut 16 passes to the left through the transfer tube 15 to light the sustainer igniter 5 and the sustainer charge 4. Gas then leaves the motor via the tube 15, the remnants of the primer 14 being blown free. A small quantity of gas passes through the port 10 in the septum 2 first lighting the auxiliary ignition material 11, the booster igniter 12 and finally the booster propellent charge 3. The gas is subsequently lost into the empty boost portion after the booster charge has burnt out.
  • a double chamber dual thrust rocket motor in which a propellant in each chamber is ignited substantially simultaneously comprising: a motor casing; a partition within said casing dividing the interior thereof into two chambers; a solid propellant charge in each of said chambers; 21 propulsion nozzle associated with each of said chamber; and means for igniting said solid propellant charges substantially simultaneously, said means including means defining a port through said partition for conducting heat energy through said partition and for restricting passage of gas therethrough to prevent any appreciable loss of pressure therethrough during burning of said propellant charges, an igniter associated with each of said propellant charges, at least one of said igniters being adjacent said port whereby ignition of the other of said igniters will ignite said one vigniter by heat energy passing through said port.
  • a rocket motor as claimed in claim 1 wherein the igniter which is adjacent said septum comprises a charge captively arranged in a container to prevent dispersion of the charge before proper ignition thereof.
  • a rocket motor as claimed in claim 1 wherein the port is sufficiently large to enable flow of gas from that side of the partition containing the propellent charge associated with the other of said igniters to assist in raising the pressure to the desired operating pressure on that side of the partition containing the propellent charge associated with said one igniter and wherein the port has an associated valve for closing the port and preventing loss of gas through the port from the lastmentioned side of the partition when the propellent charge associated with the other of said igniters is burnt out.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Air Bags (AREA)
US133659A 1960-09-15 1961-08-24 Rocket motors Expired - Lifetime US3192708A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB31883/60A GB920299A (en) 1960-09-15 1960-09-15 Improvements in rocket motors

Publications (1)

Publication Number Publication Date
US3192708A true US3192708A (en) 1965-07-06

Family

ID=10329815

Family Applications (1)

Application Number Title Priority Date Filing Date
US133659A Expired - Lifetime US3192708A (en) 1960-09-15 1961-08-24 Rocket motors

Country Status (5)

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US (1) US3192708A (cs)
CH (1) CH405829A (cs)
DE (1) DE1180578B (cs)
GB (1) GB920299A (cs)
NL (1) NL268986A (cs)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1264158B (de) * 1963-09-25 1968-03-21 Thiokol Chemical Corp Zuendvorrichtung fuer gleichzeitiges Zuenden eines Buendels von Raketentriebwerken

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
FR1058495A (fr) * 1952-06-18 1954-03-16 Soc Tech De Rech Ind Propulseur à réaction
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
FR1123880A (fr) * 1955-03-23 1956-10-01 Soc Tech De Rech Ind Propulseur
US2856851A (en) * 1955-07-27 1958-10-21 Harold E Thomas Apparatus for zoning rockets
US2939393A (en) * 1958-01-23 1960-06-07 Gen Precision Inc Vented safety squib arming device
US3008414A (en) * 1954-01-21 1961-11-14 Hotchkiss Brandt Self-propelled projectile

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
FR1058495A (fr) * 1952-06-18 1954-03-16 Soc Tech De Rech Ind Propulseur à réaction
US3008414A (en) * 1954-01-21 1961-11-14 Hotchkiss Brandt Self-propelled projectile
FR1123880A (fr) * 1955-03-23 1956-10-01 Soc Tech De Rech Ind Propulseur
US2856851A (en) * 1955-07-27 1958-10-21 Harold E Thomas Apparatus for zoning rockets
US2939393A (en) * 1958-01-23 1960-06-07 Gen Precision Inc Vented safety squib arming device

Also Published As

Publication number Publication date
NL268986A (cs)
DE1180578B (de) 1964-10-29
GB920299A (en) 1963-03-06
CH405829A (de) 1966-01-15

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